System and method for blade tip clearance control
AssigneeGeneral Electric Comapny
InventorsHenry Grady Ballard, JR., Brett Darrick Klingler
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Abstract
A system includes a turbomachine rotor having a shaft and turbomachine blades coupled to the shaft. The system also includes a turbomachine stator having a shroud surrounding the turbomachine blades of the turbomachine rotor. Further, the system includes a cooling channel having at least a first portion of the cooling channel extending upstream of a final stage of a compressor of the system, where the cooling channel is configured to receive cooled compressed air from the compressor and direct the cooled compressed air adjacent to the turbomachine rotor to reduce thermal expansion and/or axial displacement of the turbomachine rotor.
Claims20
A system, comprising:
- a turbomachine rotor comprising a shaft and turbomachine blades coupled to the shaft;
- a turbomachine stator comprising a shroud surrounding the turbomachine blades of the turbomachine rotor;
- and
- a cooling channel having at least a first portion of the cooling channel extending upstream a final stage of a compressor of the system, wherein the cooling channel is configured to receive cooled compressed air from the compressor and direct the cooled compressed air adjacent to the turbomachine rotor to reduce thermal expansion and/or axial displacement of the turbomachine rotor.
A method for reducing blade tip clearances of a turbomachine, comprising:
- diverting a first portion of compressed air to a heat exchanger during certain stages of operation of the turbomachine;
- cooling the first portion of compressed air via the heat exchanger to generate a cooled compressed air;
- routing the cooled compressed air through a channel proximate a rotor of the turbomachine, wherein the channel includes at least a first portion of the channel extending upstream of a final stage of a compressor of the turbomachine;
- and
- cooling the rotor to effectuate a reduction in thermal expansion and/or axial displacement of the rotor to reduce a blade tip clearance between a blade of the turbomachine and a stator of the turbomachine.
A turbomachine system, comprising:
- a turbomachine rotor comprising a shaft and turbomachine blades coupled to the shaft;
- a turbomachine stator comprising a shroud surrounding the turbomachine blades of the turbomachine rotor;
- a cooling channel having at least a first portion of the cooling channel extending upstream of a final stage of a compressor of the turbomachine system, wherein the cooling channel is configured to receive cooled compressed air from the compressor and direct the cooled compressed air adjacent to the turbomachine rotor to reduce thermal expansion and/or axial displacement of the turbomachine rotor;
- and
- a control system configured to selectively enable fluid communication between the compressor and the cooling channel, the control system comprising:
- a valve disposed between the compressor and the cooling channel, wherein the valve is configured to be selectively opened to enable fluid communication between the compressor and the cooling channel based on an operating condition of the turbomachine system;
- a sensor disposed proximate the cooling channel and configured to detect a parameter relating to the operating condition of the turbomachine system;
- and
- a controller configured to receive the parameter relating to the operating condition of the turbomachine system and, based on the operating condition, selectively open or close the valve to enable fluid communication between the compressor and the cooling channel.
Dependencies are inferred from the claim text.